Airflow sensing systems and apparatus
Embodiments of air flow sensing systems are provided herein. In some embodiments, one or more sensors are positionable on an aircraft and dimensioned and arranged to measure vector components of airflow velocity having at least one of a transverse or streamwise direction relative to a flight direction of the aircraft. In some embodiments, the one or more sensors are positioned in front of an aircraft wing and distributed as an array of sensors along the span of the aircraft wing.
1. An air flow sensing system, comprising:
a differential airflow probe positionable on an aircraft, the differential airflow probe having a streamwise direction and being dimensioned and arranged to measure airflow velocity vector components at least one of orthogonal or transverse to a flight direction of the aircraft and defining a first airflow channel and a second airflow channel symmetrically oriented relative to the streamwise direction, wherein each airflow channel includes a respective input port defining an airflow path through an opening and each input port is oriented at less than 90 degrees and greater than 0 degrees relative to the streamwise direction.
2. The system of claim 1 , wherein each input port defines an opening with a face that is at an angle with the airflow path greater than zero and less or equal to 90 degrees.
3. The system of claim 1 , wherein the input ports define airflow paths oriented at 90 degrees relative to the streamwise direction.
4. The system of claim 1 , wherein the input ports define airflow paths oriented at 45 degrees relative to the streamwise direction.
5. The system of claim 1 , further comprising a pressure transducer coupled to the first and second airflow channels.
6. The system of claim 5 , wherein the pressure transducer providing an output signal proportional to a pressure difference between the first and second airflow channel.
7. The system of claim 6 , wherein the output signal is proportional to a horizontal velocity component of the airflow velocity vector.
8. The system of claim 6 , wherein the output signal is proportional to a vertical velocity component of the airflow velocity vector.
9. The system of claim 1 , wherein the first and second airflow channels each define multiple openings.
10. The system of claim 1 , wherein the differential airflow probe comprises a body, and a stand-off post extending from the body.
11. The system of claim 10 , wherein the body is streamlined to minimize a distortion of airflow near the aircraft.
12. The system of claim 11 , wherein the body has a round contour in cross-section.
13. The system of claim 11 , wherein the body has a rounded contour in all cross-sections.
14. The system of claim 1 , further comprising a sensor transceiver coupled to the differential airflow probe, receiving raw input sensor signals, processing the raw input sensor signals and providing output signals.
15. The system of claim 1 , further comprising a second sensor positionable on an aircraft, the second sensor being dimensioned and arranged to measure airflow velocity vector components transverse to a flight direction of the aircraft, wherein the differential airflow probe and the second sensor are positionable in an array to form part of a sensor array on one of wing, fuselage and tail of the aircraft.
16. An air flow sensing system, comprising:
a plurality of vortex eye sensors positionable on an aircraft, the sensors being dimensioned and arranged to measure vector components of airflow velocity transverse to a flight direction of the aircraft,
wherein at least some of the sensors are positioned in front of an aircraft wing and distributed as an array of sensors along a span of the aircraft wing.
17. The system of claim 16 , wherein at least some of the sensors comprise a body having a streamwise direction and defining a first airflow channel including an input port and a second airflow channel defining an input port.
18. The system of claim 16 , further comprising a transceiver and wherein the transceiver is couple to the plurality of sensors to process raw signal input and to produce signal output.
19. The system of claim 16 , wherein the vortex eye sensors are positioned on wingtips of the aircraft at or near locations at which an anticipated position of a vortex can be determined to at least one of reduce or minimize an amount of power needed to maintain a level flight of the aircraft.
20. The system of claim 16 , further comprising a processor and a computer memory for analyzing signals from the plurality of vortex eye sensors.
21. The system of claim 16 , wherein the vortex eye sensors are arranged to measure vertical and horizontal components of the airflow near the aircraft.
22. An air flow sensing system, comprising:
a hot film airflow sensor positionable on an aircraft, the hot film airflow sensor being dimensioned and arranged to measure airflow velocity vector components at least one of orthogonal or transverse to a flight direction of the aircraft, wherein the hot film airflow sensor comprises a body having a streamwise direction and defining a through opening in the body orthogonal to the streamwise direction.
23. An air flow sensing system, comprising:
a plurality of sensors being dimensioned and arranged to measure airflow velocity vector components at least one of orthogonal or transverse to a flight direction of an aircraft, at least some of the sensors positioned on a front edge of an aircraft wing and distributed as an array of sensors along a span of the aircraft wing, wherein the plurality of sensors comprise at least one of vanes responsive to an impinging airflow or hot film airflow sensors.